Aeronautical Manufacturing Technology

关闭×

Home | About Journal | Editorial Board | Instruction | Publication Ethics Statement | Subscriptions | Contacts Us | Chinese

Office Online

Submission Online

Editor-in-chief

Journal Online

Advanced Search

Download Articles

Quick Search

2020 Vol. 63, No. 3 Published: 2020-02-01

FEATURE FORUM RESEARCH C0NTENTS COVER STORY APPROACHING SCIENCE

FEATURE

	14	Finite Element Study on Effects of Tool Wear Patterns on the Machining Process of Ti6Al4V
		XU Jinyang, HUANG Xianghui, CHEN Ming, AN Qinglong
		DOI: 10.16080/j.issn1671-833x.2020.03.014
		The effects of different tool wear patterns on the machining process of titanium alloys were investigated via the finite element simulation method. Initially, four kinds of tool wear patterns including the crater wear dominated pattern, the flank wear dominated pattern, the combined crater and flank wear dominated pattern and the edge blunting dominated pattern were established according to the actual tool wear geometrical dimensions. Then, the AdvantEdge software was used to develop the numerical models of machining Ti6Al4V using worn cemented carbide tools and to conduct the finite element analysis. The results indicate that the edge tip temperature decreases as the crater wear increases, the tensile stresses on the workpiece surface increase but the compressive stresses reduce as the flank wear increases. In the case of the combined crater and flank wear, the chip radius was decreased significantly as the tool wear extent intensifies. The edge blunting was found to have the most significant impact on the cutting forces, and the plowing effects become more pronounced when the edge radius is close to the feed rate.
		2020 Vol. 63 (3): 14-21 [Abstract] ( 372 ) HTML^New PDF (14211 KB) ( 401 )

COVER STORY

	22	New Development of Electromagnetic Pulse Forming Technology and Its Application in Aircraft Skin Parts Manufacturing
		CUI XiaoHui, ZHOU Xianglong, DU Zhihao,YU Hailiang, CHEN Baoguo
		DOI: 10.16080/j.issn1671-833x.2020.03.022
		Electromagnetic pulse forming (EMF) is a method of high-speed machining method for metal workpieces by using pulsed magnetic force. Compared with traditional processes, EMF can increase the forming limit of difficult-to-deform materials and reduce springback. Thus, it provides an effective solution to the difficult processing problem of aluminum alloy. Based on the difficult forming problems of cylindrical parts drawing, large ellipsoidal parts manufacturing, V-shaped part bending and springback control, we introduce some new technologies such as multi-directional magnetic force driving materials, magnetic field force partition loading, and high frequency oscillation effect. On this basis, the method of shaping the aircraft skin parts by magnetic field force partition loading is proposed. Experimental and simulation results show that the sheet undergoes mainly elastically deformed and results in a large springback after pure stretching. However, the elastic deformation on the sheet is transformed into plastic deformation, and the springback is greatly reduced after EMF.
		2020 Vol. 63 (3): 22-32 [Abstract] ( 419 ) HTML^New PDF (61271 KB) ( 871 )

FORUM

	36	Modeling and Real-Time Simulation of Aero-Engine and Its Control System
		ZHANG Tianhong, WU Songwei
		DOI: 10.16080/j.issn1671-833x.2020.03.036
		The application of modeling and simulation technology greatly improves the efficiency and level of aero-engine independent research and development. First, the classification of aero-engine and its control system models and simulation methods is summarized. Then, the modeling methods of aero-engine and control system are introduced along with examples. The hardware-in-the-loop and semi-physical real-time simulation test technology of control system are mainly focused. Finally, the current challenges of modeling and simulation of engines and their control systems are analyzed and prospected.
		2020 Vol. 63 (3): 36-44 [Abstract] ( 344 ) HTML^New PDF (3504 KB) ( 904 )

	45	Numerical Modeling and Simulation Analysis of Local Deformation for Aircraft Large-Walled Panel Assembly Connection
		KANG Yonggang, LI Chunsheng, CHEN Xiduo, LUO Qun,DANG Xiaojuan
		DOI: 10.16080/j.issn1671-833x.2020.03.045
		Aircraft large-walled panel is an important component of the aerodynamic shape of the aircraft. It has the characteristics of large size and weak thin wall. It is easy to produce assembly deformation during the automatic drilling and riveting assembly process, including the overall bending and torsion deformation of panel and the peripheral defects of rivet. In this paper, a large-walled panel test shows a local subsidence deformation along the long axis. The deformation problem is complicated and directly affects the subsequent assembly process. It is a problem about how to achieve strong coupling among the automatic drilling and riveting process, the rivet and its elastoplastic deformation of the connected parts. For the deformation problem, based on the constructed automatic drilling and riveting process model combined with finite element numerical simulation analysis, the simulation prediction of the structural deformation of the typical aircraft panel with multi-nail riveting assembly is carried out. Through the discussion and analysis, the process factors leading to a local deformation problem are given, which provide a theoretical basis for the optimization of the aircraft panel automatic drilling and riveting process, and the effectiveness of prediction model is verified by comparison with the experimental results.
		2020 Vol. 63 (3): 45-52 [Abstract] ( 256 ) HTML^New PDF (19521 KB) ( 234 )

	53	Geometry Optimization of Sleeve Outside Wall and Material Flow During RFSSW
		ZHAO Huaxia,LI Dengchang,WANG Yue,JI Shude
		DOI: 10.16080/j.issn1671-833x.2020.03.053
		For refill fiction stir spot welding, voids and lack of fill defects induced by insufficient material flow are easily formed at the maximum plunging position of sleeve and the movement path of sleeve. The geometry of sleeve is the main factor influencing the material flow during welding. In this paper, the outside wall of sleeve with inclined grooves were designed. On basis of the verification of rightness of finite element model by experiments, the effect of groove on material flow behavior was investigated by numerical simulation. The results show that the inclined groove can heighten the material downward flow velocity. With the increase of groove width, the material downward flow velocity decreases and the material high-speed flow area increases. When the groove width is 0.75mm, the sleeve has the most obvious effect on promoting the downward flow of material.
		2020 Vol. 63 (3): 53-58 [Abstract] ( 263 ) HTML^New PDF (23585 KB) ( 90 )

	59	Finite Element Modeling of Mechanical Response of Aluminum Alloy Materials by Laser Shock Peening
		SHU Bochao, LI Weidong,HUANG Xia, CHE Zhigang
		DOI: 10.16080/j.issn1671-833x.2020.03.059
		In order to study the dynamic mechanical properties and residual stress distribution of laser shock peening, the finite element modeling and numerical simulation of 2024–T351 laser shock peening were carried out based on ABAQUS software. The PVDF piezoelectric sensor was used to measure the spatiotemporal distribution data of laser impact force, and the dynamic pressure model of laser shock peening was established. The one-dimensional plate impact test of light-gas gun was used to verify the mechanical constitutive model of aluminum alloy 2024–T351 under ultra-high strain rate. The complex process path loading was realized based on the VDLOAD subroutine, and the nanosecond scale mechanical response characteristics during laser shock were obtained. The finite element simulation of laser shock peening was conducted, and the distribution law of residual stress in the material was analyzed. The surface residual stress test had been proceeded by drilling method. The accuracy of residual stress prediction was proven, which verified the accuracy of the established laser shock peening finite element model.
		2020 Vol. 63 (3): 59-66 [Abstract] ( 240 ) HTML^New PDF (25761 KB) ( 115 )

	67	Modeling Method of Digital Twin Models for Machining Parts
		ZOU Qi， HOU Zhixia,WANG Mingyang
		DOI: 10.16080/j.issn1671-833x.2020.03.067
		This paper introduces digital twin models for machining parts based on key features and gives the modeling method. In this paper, we propose the digital twin model with three-layer structure, including geometric layer, data layer and document layer, in order to realize machining process optimization and quality prediction. The digital twin model realizes the expression of physical parts in digital space and the information correlation with theoretical processing features. Besides, this paper also analyzes the potential application scenarios and development trends of digital twin models of machined parts.
		2020 Vol. 63 (3): 67-75 [Abstract] ( 452 ) HTML^New PDF (2049 KB) ( 698 )

	76	Temperature Field Simulation of Autoclave Forming Process Based on XFlow
		ZHANG Chenqun, BAO Yidong, AN Luling, HUAN Lei
		DOI: 10.16080/j.issn1671-833x.2020.03.076
		Aiming at the uneven temperature distribution of die surface in autoclave process, a simulation method of temperature field in autoclave process has been established based on XFlow software. Unlike the current grid-based computational fluid dynamics software, XFlow uses particle-based lattice Boltzmann method, which effectively shortens the pre-processing time. The finite element model of forced convection heat transfer of frame die in autoclave process is established by XFlow software. The average relative error between the calculated results and the experimental results is 1.83%. The reason of uneven temperature distribution of die surface in the process of forming is analyzed, and the influence of process parameters of autoclave process on the temperature field of die is discussed. The results show that the standard deviation of die surface temperature can be effectively reduced by increasing the wind speed and decreasing the heating and cooling rate.
		2020 Vol. 63 (3): 76-83 [Abstract] ( 359 ) HTML^New PDF (11910 KB) ( 277 )

RESEARCH

	86	Investigation on Spark Plasma Sintering Process of Ultra-Fine Grained WC–10%Co Cemented Carbide Three-Edged Tool
		WANG Guofeng, LIU Qing, SHI Wenzhan, LI Danfeng
		DOI: 10.16080/j.issn1671-833x.2020.03.086
		The effect of sintering temperature and holding time on the microstructures and mechanical properties of WC–10%Co cemented carbide during spark plasma sintering process was investigated. The results indicated that the densities and hardness were enhanced with the increase of sintering temperature from 1200℃ to 1350℃. The densities and hardness enhanced first and then decreased with the increase of holding time from 3min to 9min at 1350℃. The density of cemented carbide arrived maximum value of 99.3%, as well as the hardness of 2212HV at the sintering parameters of 1350℃ and 6min. The three-edged tool with high quality was sintered at the optimum parameters. The density and harness of the tool were 99.2% and 2232HV, respectively.
		2020 Vol. 63 (3): 86-91 [Abstract] ( 247 ) HTML^New PDF (9405 KB) ( 207 )

	92	Effect of γ′ Precipitation on Lamellar M₂₃C₆ Carbide Precipitation in GH4145 Alloy
		HUA Peitao,CHEN Sibo,ZHANG Weihong,YAO Xiaoyu,SUN Wenru
		DOI: 10.16080/j.issn1671-833x.2020.03.092
		The lamellar M₂₃C₆ phase is a typical harmful microstructure formed in the superalloys including GH4145. The mechanism for the precipitation of the lamellar structure has been investigated extensively, the conditions for the precipitation of the lamellar structure of the M₂₃C₆carbide, however, remains unclear till now. By analyzing the precipitation of γ′ and M₂₃C₆ phases during the cooling after the 980℃ solution and the subsequent 730℃ aging, it was found that the lamellar M₂₃C₆ precipitation was directly governed by the γ′ precipitation. After the 980℃ solution, the γ′ precipitation could be prohibited thoroughly when the cooling rate is higher than 22℃/s. During the subsequent 730℃ aging after the 980℃ solution, the M₂₃C₆ carbide precipitated as isolated particles when the γ′ phase pre-precipitated in the matrix, because the γ′ phase would inhibit the directional growth of the carbide. While the M₂₃C₆carbide might grow into lamellar form with the γ′ phase by the eutectoid reaction of (M₂₃C₆+γ′) when there was no the γ′ precipitates in the matrix before the aging. The coprecipitation of M₂₃C₆ and γ′ is the necessary conditions for the formation of the lamellar M₂₃C₆ carbide.
		2020 Vol. 63 (3): 92-102 [Abstract] ( 267 ) HTML^New PDF (13282 KB) ( 89 )

	96	Building and Application of CNC Equipment Fault Knowledge Graph
		ZHAO Qian
		DOI: 10.16080/j.issn1671-833x.2020.03.096
		he causes of CNC equipment fault are complicated, concealed and difficult to be investigated. To realize the accumulation, organization and sharing of the historical cases of CNC equipment fault, the method of constructing vertical knowledge graph was put forward. Firstly, the data-driven incremental construction technology is used to build CNC equipment fault ontology model. Then the data-mapping mechanism based on mode, which transform related database data into resource description framework data for storage, is proposed. Based on this, the visualization, management and application of the knowledge graph are realized. Finally, knowledge graph construction system in CNC equipment fault field is developed and the validity and rationality of the knowledge graph construction method is verified. Practice has proven that the construction of knowledge graph to the fault data accumulation, organization, fault reasoning and fault diagnosis on the field of CNC equipment fault has some guiding significance.
		2020 Vol. 63 (3): 96-102 [Abstract] ( 584 ) HTML^New PDF (3095 KB) ( 1042 )

Notices

Download

	Copyright Transfer Agreement

Links

	AVIC Manufacturing Technology Institute

	AVIC

Copyright © Editorial Board of Aeronautical Manufacturing Technology
Supported by: Beijing Magtech